US8502126B2 - System and method for navigating an object - Google Patents
System and method for navigating an object Download PDFInfo
- Publication number
- US8502126B2 US8502126B2 US12/789,172 US78917210A US8502126B2 US 8502126 B2 US8502126 B2 US 8502126B2 US 78917210 A US78917210 A US 78917210A US 8502126 B2 US8502126 B2 US 8502126B2
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- Prior art keywords
- guided projectile
- mach
- time
- projectile
- navigation system
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G7/00—Direction control systems for self-propelled missiles
- F41G7/008—Combinations of different guidance systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G7/00—Direction control systems for self-propelled missiles
- F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
- F41G7/22—Homing guidance systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G7/00—Direction control systems for self-propelled missiles
- F41G7/34—Direction control systems for self-propelled missiles based on predetermined target position data
- F41G7/36—Direction control systems for self-propelled missiles based on predetermined target position data using inertial references
Definitions
- Embodiments pertain to a system and method for detecting when an object accelerates through mach one.
- An accurate determination of velocity is critical in order to navigate objects such as projectiles and missiles to a desired point in space.
- Existing systems and methods often use a GPS receiver to determine velocity.
- GPS systems add to the cost of producing projectiles and missiles.
- many projectiles and/or missiles are used in applications where the mission timelines are too short to use GPS.
- One method of estimating the initial velocity of a projectile or missile is to characterize the launch velocity versus the temperature of the object's propellant charge and/or the launch chamber pressure.
- FIG. 1 illustrates an example projectile engagement scenario where the projectile exceeds mach one during flight.
- FIG. 2 illustrates a flow diagram of an example method of detecting when an object accelerates through mach one.
- FIG. 3 illustrates example acceleration data that may be collected during a flight of an object that accelerates through mach one.
- FIG. 4 illustrates an example plot of jerk data that may be created from the data shown in FIG. 3 .
- FIG. 5 illustrates an example plot of the jerk data shown in FIG. 4 where the jerk data has been filtered.
- FIG. 6 illustrates the example plot shown in FIG. 5 and includes data that may be used in determining the time at which the object accelerates through mach one.
- FIG. 7 shows a plot of a projectile's velocity versus time as measured by radar as well as results for one example projectile test conducted using the example systems and methods described herein.
- FIG. 8 shows an example system for determining when an object accelerates through mach one during flight.
- the systems and methods described herein establish the velocity of a missile or projectile at a point in time by detecting when the missile or projectile accelerates through the speed of sound.
- the system and method may calculate the velocity of the missile or projectile when the missile or projectile accelerates through the speed of sound transition.
- This information relating to the object's velocity at a specific point in time may be provided to a guidance system (e.g., an Inertial Measurement Unit) on the object which utilizes the information to navigate the object.
- an object that accelerates through the speed of sound refers to a guided projectile, projectile, missile, mortar, bomb, plane, spacecraft or any other device that accelerates through mach one.
- FIG. 1 illustrates an example projectile engagement scenario 100 where the projectile exceeds mach one during flight. It should be noted that the projectile typically accelerates through mach one in the fly-out phase of the projectile engagement scenario.
- FIG. 2 illustrates a flow diagram of an example method 200 of navigating an object.
- the method 200 includes [ 201 ] detecting when the object accelerates through the speed of sound and [ 209 ] maneuvering the object based on when the object accelerates through the speed of sound.
- the method 200 may further include [ 207 ] calculating the velocity at which the object is moving when the object accelerates through the speed of sound.
- [ 207 ] calculating the velocity at which the object is moving when the object accelerates through the speed of sound includes [ 214 ] determining the temperature of an environment that the object is traveling through.
- the accuracy of the velocity calculation may be improved by also [ 214 ] determining the humidity, pressure and air density of the environment that the object is traveling through.
- the method 200 may further include [ 204 ] creating a projected flight plan for the object where the projected flight plan includes an estimate as to how long after launch the object will accelerate through the speed of sound and at what velocity the object will be traveling as the object accelerates through the speed of sound.
- [ 209 ] maneuvering the object based on when the object accelerates through the speed of sound includes [ 206 ] comparing the measured time the object accelerates through the speed of sound with the estimated time the object was supposed to accelerate through the speed of sound.
- maneuvering the object based on when the object accelerates through the speed of sound may also include [ 216 ] comparing the measured velocity of the object as the object accelerates through the speed of sound with the estimated velocity that the object was supposed to be traveling when the object accelerated through the speed of sound and adjusting the flight of the object.
- [ 201 ] detecting when the object accelerates through the speed of sound includes measuring the acceleration of the object (e.g., with an accelerometer). It should be noted that any known method of measuring the acceleration of the object may be used in the method 200 .
- [ 201 ] detecting when the object accelerates through the speed of sound includes (i) [ 208 ] computing the jerk of the object during flight based on the measured acceleration; (ii) [ 210 ] filtering the jerk; and (iii) [ 212 ] calculating the speed of sound transition time based on the filtered jerk.
- FIG. 3 shows example acceleration data that may be obtained by an accelerometer measurement located along the projectile body centerline (i.e., x-axis).
- the plot shows that the rate of changing acceleration is altered as the object accelerates through mach one. This alteration is indentified in FIG. 3 as an SoS transition.
- FIG. 4 shows a plot identifying the derivative of acceleration (i.e., jerk) that was calculated based on the data shown in FIG. 3 .
- the jerk provides an indication as to when the projectile passes through the speed of sound transition (discussed more below).
- the jerk may be calculated with a digital difference algorithm.
- the jerk may be determined more accurately by selecting the appropriate period (m) to determine the jerk.
- the period (m) may be chosen to be approximately the number of time samples that are necessary to transition through the speed of sound.
- V SoS 331.5* ⁇ square root over ( 1 +T /273.15) ⁇ Pressure, humidity and air density can also be used, if known, for a more accurate calculation of V SoS .
- FIG. 7 shows a plot of a projectile's velocity versus time as measured by radar as well as results for one example projectile test.
- the calculated T SoS , V SoS have been added to the plot from integrated accelerometer measurements that are used with the example systems and methods described herein.
- FIG. 8 shows an example system 300 for navigating an object 310 .
- the system 300 includes a detector 320 within the object 310 .
- the detector 320 determines when the object 310 accelerates through mach one.
- the system 300 further includes a guidance system 330 within the object 310 .
- the guidance system 330 adjusts the flight of the object 310 based on data received from the detector 320 .
- the detector 320 is an inertial measurement unit 320 that includes an accelerometer which measures acceleration of the object 310 during flight. It should be noted that the accelerometer is preferably located along an x-axis of the object 310 . In addition, as described above with regard to FIG. 4 , the inertial measurement unit 320 determines the jerk of the object 310 during flight. The inertial measurement unit 320 may then filter the measured jerk (see, e.g., plot shown in FIG. 5 ) before determining the time when the object 310 accelerates through the speed of sound based on the filtered jerk (see FIG. 6 ).
- the guidance system 330 Based on the measured time that the inertial measurement unit 320 determines the object 310 accelerates through the speed of sound, the guidance system 330 adjusts the flight of the object 310 in order to direct the object 310 to a desired location. It should be noted that in some embodiments, the guidance system 330 may also adjust the flight of the object 310 based on a calculated velocity that is obtained from the inertial measurement unit 320 and the calculated speed of sound. Providing the calculated velocity to the guidance system 330 is beneficial to navigating the object 310 because the speed of sound varies depending on the temperature, pressure, humidity and air density of the environment where the object 310 is traveling.
- the systems and methods described herein may be used with guided projectiles and missiles that attain velocities greater than the speed of sound and are used in relatively long time line missions.
- the systems and methods are able to monitor the physical phenomenon of an object accelerating through mach one in order to facilitate navigation of an object by determining the velocity of the object at a point in time (i.e., when the object accelerates through mach one) without using GPS or radar.
Abstract
Description
Jerk_Filter(n)=mean(Jerk(n−c/2:n+c/2)).
T SoS=(W 1·(T Center −T 1)+W 2·(T Begin −T 2))/(W+W 2).
V SoS=331.5*√{square root over (1 +T/273.15)}
Pressure, humidity and air density can also be used, if known, for a more accurate calculation of VSoS.
Claims (7)
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US12/789,172 US8502126B2 (en) | 2010-05-27 | 2010-05-27 | System and method for navigating an object |
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US12/789,172 US8502126B2 (en) | 2010-05-27 | 2010-05-27 | System and method for navigating an object |
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US20110290932A1 US20110290932A1 (en) | 2011-12-01 |
US8502126B2 true US8502126B2 (en) | 2013-08-06 |
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Cited By (5)
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US20140131508A1 (en) * | 2006-09-29 | 2014-05-15 | Lone Star Ip Holdings, Lp | Small smart weapon and weapon system employing the same |
US8997652B2 (en) | 2003-05-08 | 2015-04-07 | Lone Star Ip Holdings, Lp | Weapon and weapon system employing the same |
US9006628B2 (en) | 2005-09-30 | 2015-04-14 | Lone Star Ip Holdings, Lp | Small smart weapon and weapon system employing the same |
US9068803B2 (en) | 2011-04-19 | 2015-06-30 | Lone Star Ip Holdings, Lp | Weapon and weapon system employing the same |
US9550568B2 (en) | 2006-10-26 | 2017-01-24 | Lone Star Ip Holdings, Lp | Weapon interface system and delivery platform employing the same |
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CN105258698B (en) * | 2015-10-13 | 2017-12-19 | 北京航天控制仪器研究所 | A kind of high dynamic spin aerial Combinated navigation method of guided cartridge |
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Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8997652B2 (en) | 2003-05-08 | 2015-04-07 | Lone Star Ip Holdings, Lp | Weapon and weapon system employing the same |
US9006628B2 (en) | 2005-09-30 | 2015-04-14 | Lone Star Ip Holdings, Lp | Small smart weapon and weapon system employing the same |
US20140131508A1 (en) * | 2006-09-29 | 2014-05-15 | Lone Star Ip Holdings, Lp | Small smart weapon and weapon system employing the same |
US9068796B2 (en) * | 2006-09-29 | 2015-06-30 | Lone Star Ip Holdings, Lp | Small smart weapon and weapon system employing the same |
US9550568B2 (en) | 2006-10-26 | 2017-01-24 | Lone Star Ip Holdings, Lp | Weapon interface system and delivery platform employing the same |
US10029791B2 (en) | 2006-10-26 | 2018-07-24 | Lone Star Ip Holdings, Lp | Weapon interface system and delivery platform employing the same |
US9068803B2 (en) | 2011-04-19 | 2015-06-30 | Lone Star Ip Holdings, Lp | Weapon and weapon system employing the same |
US9784543B2 (en) | 2011-04-19 | 2017-10-10 | Lone Star Ip Holdings, Lp | Weapon and weapon system employing the same |
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US20110290932A1 (en) | 2011-12-01 |
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